Transition of the boundary layer on a flat plate at supersonic and hypersonic velocities
V.I. Kornilov1
1Khristianovich Institute of Theoretical and Applied Mechanics SB RAS
Keywords: transition of the boundary layer, supersonic and hypersonic velocities, flat plate, generalization of experimental data
Pages: 365-373
Abstract
The transition of the boundary layer from the laminar to the turbulent state on a smooth flat plate at a zero angle of attack is studied in the range of Mach numbers М∞ = 2−6. It is demonstrated that the results measured at the end of the transition region can be approximated by a simple dependence suitable for applications, which does not require additional measurements, is valid in the range of Mach numbers М∞ = 2−10, and, with an error lower than 20 %, can be used to estimate the location of the transition region on a flat plate in geometrically similar wind tunnels.
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